US4642997A - Process and apparatus for power-and air conditioning-fresh air generation in aircraft - Google Patents

Process and apparatus for power-and air conditioning-fresh air generation in aircraft Download PDF

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Publication number
US4642997A
US4642997A US06/717,377 US71737785A US4642997A US 4642997 A US4642997 A US 4642997A US 71737785 A US71737785 A US 71737785A US 4642997 A US4642997 A US 4642997A
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US
United States
Prior art keywords
air
conditioning compressor
power unit
auxiliary power
set forth
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Expired - Lifetime
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US06/717,377
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English (en)
Inventor
Herfried Krafka
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Airbus Defence and Space GmbH
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Deutsche Aerospace AG
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Assigned to DEUTSCHE AIRBUS GMBH reassignment DEUTSCHE AIRBUS GMBH ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: HERFRIED, KRAFKA, HERFRIED
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0622—Environmental Control Systems used in combination with boundary layer control systems
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency

Definitions

  • the invention is directed to a process and a device for power- and air conditioning-fresh air generation in aircraft, which are equipped with main power plants and an auxiliary power unit driving an air conditioning compressor with an appropriate air intake, compressor, diffuser and an associated exhaust nozzle as well as a heat exchanger and which comprise a suction device for removing the boundary layer from aircraft wings.
  • auxiliary power unit in the tail of aircraft for generation of electrical current and for the supply of air conditioned ambient air to the aircraft is known, whereby the auxiliary power unit assumes this task only during the periods, when the aircraft is on the ground during loading and unloading and during fueling and while the main power plants are not in operation.
  • the auxiliary power unit is shut down in flight and the main power units assume the task of power and fresh air supply.
  • auxiliary power and air conditioning unit which has a variable geometry compressor, which can be driven on the one hand by bleed air from the main power plant and on the other hand through a freewheeling clutch by the auxiliary power unit for power- and air conditioning-fresh air supply.
  • the device has the disadvantage that for its operation a high fuel consumption is required, because without additional power supply this is always proportional to the output, which the main power plants must generate for the required bleed air amount or the auxiliary power unit must supply as mechanical output for the pertinent supply functions of the aircraft.
  • the compressor stages of the main power plants are primarily optimized for the generation of forward thrust and not for the production of bleed air, whereby for this additional air mass the entire main power plant has to be designed to be larger.
  • the main power plants are very highly loaded by the removal of bleed air, particularly during the take-off phase and thus the flight safety of the aircraft is jeopardized.
  • FIG. 1 a section through the device for the power and air conditioning fresh air generation in schematic presentation
  • FIG. 2 a section through the air conditioning air compressor.
  • a guidance tube 5 equipped with a nozzle 8 is arranged in the air intake 4, at whose other end a feed tube 32 for cabin exhaust air and a pipeline 33 for exhaust air from the boundary layer suction device, not shown here, from the wing surfaces of the aircraft, also not shown here, is provided.
  • this exhaust air is accelerated by the nozzle 8 towards the mid-section of of the intake 4 and subsequently mixed together in the collection duct 6 with the fresh air flowing in through the air intake 4, whereby the pressure difference existing at the intake throat 6a or respectively at the nozzle outlet 8 increases the flow velocity.
  • the mixture of the exhaust air with the fresh air occurs in the subsequently arranged diffuser 7.
  • auxiliary power unit arranged in the airplane tail 34 for the purpose of its efficient operation.
  • the auxiliary power unit is therefore constantly kept in operation during the aircraft operation on the ground as well as in the air.
  • a portion of the fresh air from the air intake 4 is aspirated through a feed duct 9 by an air conditioning compressor 2 coupled with the compressor or turbine 17 through a clutch 31 and is compressed in the air conditioning compressor 2 for supply of fresh air for air conditioning.
  • the air-conditioning air from the pipe 15 can together with the heated air conditioning air from the heat exchanger 11 according to the heat requirements be subsequently mixed at the crossing of the pipe 15 and a return pipe 12 and be further directed into the cabin.
  • the heat exchanger 11 is arranged at the wall of the exhaust nozzle 3 of the auxiliary power unit 1 for the absorption of heat from the exhaust gases.
  • a controlled portion or the entire amount of the exhaust air from the cabin and/or from the boundary layer suction can be directed by the guide tube 5 through a feed pipe 19 to a turbine 20 disengageably connected with the air conditioning compressor 2 through a clutch 29.
  • the exhaust gases are exhausted through an exhaust pipe not shown here.
  • the control of the amount of exhaust air, which is accelerated by means of an additional nozzle 24 at the feed pipe 5 to the turbine, is accomplished by means of a flap 28 arranged at said feed pipe.
  • the supply of exhaust air from the cabin and from the boundary layer suction can be also controlled separately or collectively by means of an additional flap 25 designed as a double barrier at the supply pipe 32 and the pipeline 33.
  • an additional flap 26 is arranged at the guide tube 5 for controlling the exhaust air to the air conditioning compressor 2.
  • a control connection 42 is provided between the flaps 25, 26, 28 and an intake flap 30 located at the air intake 4, whereby said control connection leads to a known and therefore not shown in detail control device 43, by means of which the respectively required mass of exhaust air and fresh air is controllable by the above-mentioned flaps in an interdependent manner.
  • annular chamber 36 can be assigned to a first stage 21 of the air conditioning compressor 2, which on the one hand comprises a gap 38 for entry of fresh air from the stator duct 37 which has already been compressed by the air conditioning compressor 2 and on the other hand comprises an exit 39 for the outflow to the heat exchanger 11 or to the cabin.
  • a further annular chamber 41 can be provided at said compressor with an entry 40 for the exhaust air flowing from the guide tube 5, which through an access 44 acts on the additional stages 22 of the air conditioning compressor 2, whereby it can be operated extremely economically in case of minor output requirements.
  • the compressor 17 of the auxiliary power unit 1 also designed in a like manner or of the main power plant not shown here--which like the first-mentioned one can be of centrifugal or axial construction--can be used, whose other stages 22 for power unit operation, however, must be supplied with an exhaust-fresh air mixture or only with fresh air.
  • the advantage of the invention is particularly justified in that, for the purpose of a considerable fuel economy or for a considerable power increase at equal consumption, the air conditioning exhaust air from the passenger and/or pilot cabin is utilized as energy-rich combustion air for the efficient operation of the auxiliary power unit.
  • This exhaust air has only lost a small portion of its oxygen content in the cabin, has however still a large heat content and, because of the general simulation requirement of creating at great flight altitudes by air pressure a relatively low atmospheric altitude in the cabin for the passengers, it has a high quantity of compression energy.
  • This exhaust air rich in energy can therefore be utilized for driving a turbine coupled with the air conditioning compressor for a particularly high output requirement, as well as for the supply of the compressor of the auxiliary power unit and for the intermittent or continuous drive of the air conditioning compressor by means of its stages provided therefor, whereby in the last case a particularly economic operation of this unit in case of a small output requirement is possible.
  • the likewise very power-rich exhaust air from the boundary layer suction can be drawn upon for operating the auxiliary power unit or the turbine and/or for economic generation of air conditioning fresh air in the air conditioning compressor or in the device for boundary layer suction, because this exhaust air has, in addition to a high compression energy, also a high oxygen content.
  • an optimum adaptation of the device to the operational requirements of an efficient and economical power- and air conditioning air generation is always possible by means of the control or regulation of the respectively required amount of exhaust air and fresh air through flaps, which are controllable by a control device, as well as by declutching of non-required rotating accessory components, as for instance the turbine.

Landscapes

  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Compressors, Vaccum Pumps And Other Relevant Systems (AREA)
  • Air-Conditioning For Vehicles (AREA)
US06/717,377 1984-03-31 1985-03-29 Process and apparatus for power-and air conditioning-fresh air generation in aircraft Expired - Lifetime US4642997A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3412101A DE3412101A1 (de) 1984-03-31 1984-03-31 Einbauanordnung eines hilfstriebwerkes im rumpfheck von transportflugzeugen zur wirtschaftlichen erzeugung von klimaluft und von vortriebsschub im flug
DE3412101 1984-03-31

Publications (1)

Publication Number Publication Date
US4642997A true US4642997A (en) 1987-02-17

Family

ID=6232270

Family Applications (1)

Application Number Title Priority Date Filing Date
US06/717,377 Expired - Lifetime US4642997A (en) 1984-03-31 1985-03-29 Process and apparatus for power-and air conditioning-fresh air generation in aircraft

Country Status (7)

Country Link
US (1) US4642997A (it)
DE (1) DE3412101A1 (it)
ES (1) ES8703375A1 (it)
FR (1) FR2563491B1 (it)
GB (1) GB2158937B (it)
IT (1) IT1183496B (it)
NL (1) NL8500916A (it)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5123242A (en) * 1990-07-30 1992-06-23 General Electric Company Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
WO2005063565A1 (en) * 2003-12-29 2005-07-14 Airbus Deutschland Gmbh Method and device for suctioning the boundary layer
GB2419640A (en) * 2004-10-26 2006-05-03 Boeing Co Dual flow inlet for auxiliary power unit (APU)
US20070266707A1 (en) * 2004-05-13 2007-11-22 Airbus Deutschland Gmbh Boundary Layer Suction Arrangement
US20090008505A1 (en) * 2004-05-13 2009-01-08 Airbus Deutschland Gmbh Aircraft with a fluid-duct-system
US20130077329A1 (en) * 2011-09-26 2013-03-28 Andre Hessling Aircraft light
US20170037779A1 (en) * 2014-12-15 2017-02-09 Rolls-Royce Corporation Aircraft boundary layer removal with auxilliary power unit suction
US10384799B2 (en) * 2013-10-31 2019-08-20 Safran Power Units Method and system for generating auxiliary power in an aircraft
US10988262B2 (en) 2018-03-14 2021-04-27 Honeywell International Inc. Cabin pressure control system architecture using cabin pressure air for inlet to APU core compressor
US11273917B2 (en) 2018-05-29 2022-03-15 Honeywell International Inc. Cabin discharge air management system and method for auxiliary power unit
US11511865B2 (en) 2018-05-29 2022-11-29 Honeywell International Inc. Air supply management system for auxiliary power unit

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3633090A1 (de) * 1986-09-29 1988-04-07 Kloeckner Humboldt Deutz Ag Hilfsgasturbinenanlage
US5114103A (en) * 1990-08-27 1992-05-19 General Electric Company Aircraft engine electrically powered boundary layer bleed system
GB2248682B (en) * 1990-09-28 1994-08-10 Gilberts Apparatus for controlling air flow in ductwork
US6735953B1 (en) * 1997-12-22 2004-05-18 Allied Signal Inc. Turbomachine-driven environmental control system
FR2839948B1 (fr) * 2002-05-22 2004-12-17 Airbus France Echangeur pour circuit de conditionnement d'air d'aeronef et ensemble de propulsion integrant un tel echangeur

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2304151A (en) * 1939-03-13 1942-12-08 Robert B P Crawford Air conditioning system
US2697917A (en) * 1951-09-15 1954-12-28 Garrett Corp Air conditioning apparatus for enclosures of aircraft
US2829505A (en) * 1955-04-27 1958-04-08 Lockheed Aircraft Corp Systems for preventing ice formation
US2929224A (en) * 1955-12-23 1960-03-22 Garrett Corp Gas turbine compressor driven air conditioning system
US2940258A (en) * 1954-01-25 1960-06-14 Rolls Royce Supplying air to internal components of engines
US3052106A (en) * 1960-05-19 1962-09-04 Thompson Ramo Wooldridge Inc Air cooling system
US3247676A (en) * 1965-01-14 1966-04-26 Rosemount Eng Co Ltd Aerodynamic cooling
DE1456146A1 (de) * 1964-04-29 1968-12-12 Hawker Siddeley Dynamics Ltd Klimaanlage,insbesondere fuer ein Flugzeug
US3470703A (en) * 1968-01-16 1969-10-07 Lian Tong Wen Hypersonic cooling device
US3688770A (en) * 1970-10-08 1972-09-05 Westinghouse Electric Corp High pressure gas pressurization system
US3699777A (en) * 1971-04-09 1972-10-24 United Aircraft Corp Capacity control for gas turbine powered air cycle refrigeration system
US4014179A (en) * 1975-08-29 1977-03-29 The Garrett Corporation Air conditioning system for aircraft
US4374469A (en) * 1980-12-24 1983-02-22 United Technologies Corporation Variable capacity air cycle refrigeration system

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2304151A (en) * 1939-03-13 1942-12-08 Robert B P Crawford Air conditioning system
US2697917A (en) * 1951-09-15 1954-12-28 Garrett Corp Air conditioning apparatus for enclosures of aircraft
US2940258A (en) * 1954-01-25 1960-06-14 Rolls Royce Supplying air to internal components of engines
US2829505A (en) * 1955-04-27 1958-04-08 Lockheed Aircraft Corp Systems for preventing ice formation
US2929224A (en) * 1955-12-23 1960-03-22 Garrett Corp Gas turbine compressor driven air conditioning system
US3052106A (en) * 1960-05-19 1962-09-04 Thompson Ramo Wooldridge Inc Air cooling system
DE1456146A1 (de) * 1964-04-29 1968-12-12 Hawker Siddeley Dynamics Ltd Klimaanlage,insbesondere fuer ein Flugzeug
US3247676A (en) * 1965-01-14 1966-04-26 Rosemount Eng Co Ltd Aerodynamic cooling
US3470703A (en) * 1968-01-16 1969-10-07 Lian Tong Wen Hypersonic cooling device
US3688770A (en) * 1970-10-08 1972-09-05 Westinghouse Electric Corp High pressure gas pressurization system
US3699777A (en) * 1971-04-09 1972-10-24 United Aircraft Corp Capacity control for gas turbine powered air cycle refrigeration system
US4014179A (en) * 1975-08-29 1977-03-29 The Garrett Corporation Air conditioning system for aircraft
US4374469A (en) * 1980-12-24 1983-02-22 United Technologies Corporation Variable capacity air cycle refrigeration system

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
US5123242A (en) * 1990-07-30 1992-06-23 General Electric Company Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
WO2005063565A1 (en) * 2003-12-29 2005-07-14 Airbus Deutschland Gmbh Method and device for suctioning the boundary layer
US7757994B2 (en) 2003-12-29 2010-07-20 Airbus Deutschland Gmbh Method and device for suctioning the boundary layer
US7837155B2 (en) 2004-05-13 2010-11-23 Airbus Deutschland Gmbh Boundary layer suction arrangement
US20070266707A1 (en) * 2004-05-13 2007-11-22 Airbus Deutschland Gmbh Boundary Layer Suction Arrangement
US7988102B2 (en) * 2004-05-13 2011-08-02 Airbus Deutschland Gmbh Aircraft with a fluid-duct-system
US20090008505A1 (en) * 2004-05-13 2009-01-08 Airbus Deutschland Gmbh Aircraft with a fluid-duct-system
GB2419640A (en) * 2004-10-26 2006-05-03 Boeing Co Dual flow inlet for auxiliary power unit (APU)
GB2419640B (en) * 2004-10-26 2008-05-21 Boeing Co Dual flow apu inlet and associated systems and methods
US20130077329A1 (en) * 2011-09-26 2013-03-28 Andre Hessling Aircraft light
US9132923B2 (en) * 2011-09-26 2015-09-15 Goodrich Lighting Systems Gmbh Aircraft light
US9771168B2 (en) 2011-09-26 2017-09-26 Goodrich Lighting Systems Gmbh Aircraft light
US10384799B2 (en) * 2013-10-31 2019-08-20 Safran Power Units Method and system for generating auxiliary power in an aircraft
US20170037779A1 (en) * 2014-12-15 2017-02-09 Rolls-Royce Corporation Aircraft boundary layer removal with auxilliary power unit suction
US10988262B2 (en) 2018-03-14 2021-04-27 Honeywell International Inc. Cabin pressure control system architecture using cabin pressure air for inlet to APU core compressor
US11273917B2 (en) 2018-05-29 2022-03-15 Honeywell International Inc. Cabin discharge air management system and method for auxiliary power unit
US11511865B2 (en) 2018-05-29 2022-11-29 Honeywell International Inc. Air supply management system for auxiliary power unit

Also Published As

Publication number Publication date
IT1183496B (it) 1987-10-22
IT8520107A0 (it) 1985-03-27
GB2158937A (en) 1985-11-20
FR2563491B1 (fr) 1989-02-03
ES8703375A1 (es) 1987-02-16
GB2158937B (en) 1987-11-04
FR2563491A1 (fr) 1985-10-31
DE3412101A1 (de) 1985-10-10
NL8500916A (nl) 1985-10-16
GB8508024D0 (en) 1985-05-01
ES541772A0 (es) 1987-02-16

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